Application of differential evolution algorithm in the problems of gliding descent optimization

Abstract

Despite the closure of the Space Shuttle program, spaceplane remain a promising vehicle, which is being developed in many countries, such as USA, European Union and China. Interest in spaceplane is due to the possibility of their reusability and wider maneuverability in comparison with reentry capsule. However, it’s reusability is directly related to satisfying the temperature limit while descending from orbit. Also, the spaceplane has ricochets in its trajectory due to a high lift-to-drag ratio that decreases landing accuracy. The paper aim is the synthesis of an optimal control program in the problems of gliding descent to the maximizing longitudinal range and lateral range with temperature limitation and the absence of ricochets. The synthesis of the optimal trajectory can be obtained by the control channels of attack angle and bank angle. The approach is to represent the control channels of attack angle and bank angle in the form of Fourier series, and the search for the optimal solution is carried out using the differential evolution algorithm. The paper presents the results of solving problems using a different number of the Fourier series terms.